US20090235634A1 - System for extending the turndown range of a turbomachine - Google Patents
System for extending the turndown range of a turbomachine Download PDFInfo
- Publication number
- US20090235634A1 US20090235634A1 US12/053,921 US5392108A US2009235634A1 US 20090235634 A1 US20090235634 A1 US 20090235634A1 US 5392108 A US5392108 A US 5392108A US 2009235634 A1 US2009235634 A1 US 2009235634A1
- Authority
- US
- United States
- Prior art keywords
- air
- exhaust
- gas
- inlet
- hrsg
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
Links
- 238000010438 heat treatment Methods 0.000 claims abstract description 13
- 239000000446 fuel Substances 0.000 claims description 22
- 239000012530 fluid Substances 0.000 claims description 21
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 10
- 238000002485 combustion reaction Methods 0.000 claims description 7
- 238000011084 recovery Methods 0.000 claims description 5
- 238000000034 method Methods 0.000 claims description 4
- 238000011144 upstream manufacturing Methods 0.000 claims description 3
- 238000006243 chemical reaction Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 58
- 230000007423 decrease Effects 0.000 description 3
- 238000010304 firing Methods 0.000 description 2
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 238000004378 air conditioning Methods 0.000 description 1
- -1 but not limiting of Substances 0.000 description 1
- 239000000567 combustion gas Substances 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000000605 extraction Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 239000003345 natural gas Substances 0.000 description 1
- 238000012856 packing Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/08—Heating air supply before combustion, e.g. by exhaust gases
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
- F02C6/18—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E20/00—Combustion technologies with mitigation potential
- Y02E20/14—Combined heat and power generation [CHP]
Definitions
- the present invention relates to the operation of a turbomachine, and more particularly to a system for extending the turndown range by heating the inlet-air.
- Turbomachines such as gas turbines, aero-derivatives, or the like, commonly operate in a combined-cycle and/or cogeneration mode.
- a heat recovery steam generator which generates steam, receives the exhaust-gas from the turbomachine; the steam then flows to a steam turbine that generates additional electricity.
- a portion of the steam generated by the heat recovery steam generator is sent to a separate process requiring the steam.
- Combined-cycle and cogeneration plants are rated to generate the maximum amount of energy (mechanical, electrical, etc) while operating at baseload.
- baseload operation though desired by operators, is not always feasible.
- the powerplant must either shutdown or operate at partload, where less than the maximum amount of energy is generated.
- Turbomachines are typically required to maintain emissions compliance while generating power.
- a turbomachine operating at partload may not maintain emissions compliance over the entire partload range, (from spinning reserve to near baseload).
- Turndown range may be considered the loading range where the turbomachine maintains emissions compliance.
- a broad turndown range allows operators to maintain emissions compliance, minimize fuel consumption, and avoid the thermal transients associated with shutting down the powerplant.
- the system should reduce the fuel consumed by the turbomachine while operating at the partload range.
- the system should not require significant changes to the turbomachine.
- a system for extending a turndown range of a turbomachine operating at partload comprising: a turbomachine comprising a compressor, which receives an inlet-air; a combustion system; and a turbine section; wherein the turbomachine produces an exhaust-gas; a heat recovery steam generator (HRSG), wherein the HRSG receives a portion of the exhaust-gas and produces steam; and at least one air preheater comprising at least one heat exchanging section, wherein the at least one air preheater heats the inlet-air before the inlet-air flows to the compressor; wherein a portion of the at least one heat exchanging section receives a fluid at a temperature allowing for heating of the inlet-air; and wherein the fluid flows from a source external to the turbomachine; and wherein heating the inlet-air reduces an output of the turbomachine and extends the turndown range.
- HRSG heat recovery steam generator
- FIG. 1 is a schematic illustrating an example of a system for extending the turndown range of a turbomachine in accordance with a first embodiment of the present invention.
- FIG. 2 is a schematic illustrating an example of a system for extending the turndown range of a turbomachine in accordance with a second embodiment of the present invention.
- FIG. 3 is a schematic illustrating an example of a system for extending the turndown range of a turbomachine in accordance with a third embodiment of the present invention.
- FIG. 4 is a schematic illustrating an example of a system for extending the turndown range of a turbomachine in accordance with a fourth embodiment of the present invention.
- the present invention may be applied to a wide variety of turbomachines including, but not limiting of, gas turbines, aero-derivative combustion turbines, and the like.
- An embodiment of the present invention takes the form of an application and process that may heat the air entering a turbomachine (hereinafter “gas turbine”) to increase the turndown range.
- An embodiment of the present invention has the technical effect of extending the turndown range by heating the air (hereinafter “inlet-air”) entering the compressor of the gas turbine. As described below, the inlet-air is heated by an energy source external to the gas turbine.
- FIG. 1 is a schematic illustrating an example of a system 100 for extending the turndown range of a gas turbine 105 in accordance with a first embodiment of the present invention.
- FIG. 1 illustrates a site comprising a gas turbine 105 : a heat recovery steam generator (HRSG) 110 ; a stack 115 ; and an air preheater 155 .
- the gas turbine 105 comprises an axial flow compressor 120 having a shaft 125 .
- Inlet-air 130 enters the compressor 120 , is compressed and then discharged to a combustion system 135 , where a fuel 140 , Such as natural gas, is burned to provide high-energy combustion gases which drives the turbine section 145 .
- a fuel 140 Such as natural gas
- the energy of the hot gases is converted into work, some of which is used to drive the compressor 120 through the shaft 125 , with the remainder available for useful work to drive a load such as the generator, mechanical drive, or the like (none of which are illustrated).
- the exhaust-gas 150 from the turbine section 145 may then flow to the HRSG 110 , which may transfer a portion of the exhaust-gas 150 energy into steam (not illustrated).
- the combustion system 135 may ensure that the exhaust-gas 150 flowing out of the stack 115 meets the site emissions requirements.
- certain partload operations may violate the site emissions requirements, which may require the shutdown of the gas turbine 105 .
- An increase in the turndown range may avoid the need to shutdown the gas turbine 105 .
- an extended turndown range allows for operating the gas turbine 105 at lower loads, while maintaining emissions compliance and consuming less fuel 140 .
- the present invention extends the turndown range by heating the inlet-air 130 .
- the output (electrical, mechanical, or the like) of a gas turbine 105 is governed by the amount of mass-flow entering the compressor 120 .
- the mass-flow may be considered the product of the density and the volume-flow of the inlet-air 130 entering the compressor 120 .
- the amount of volume-flow entering the compressor 120 may vary on the ambient temperature conditions and the angle of Variable Inlet Guide Vanes (IGVs), if present on the gas turbine 105 .
- the IGV angle may determine the flow area at the inlet of the compressor 120 .
- the IGV angle may be reduced to a minimum angle, limiting the amount of turndown. At the minimum IGV angle, a corresponding minimum volume-flow is drawn into the compressor 120 .
- the heating of the inlet-air 130 decreases the density, allowing less dense inlet-air 130 to enter the compressor 120 .
- the volume-flow entering the compressor 120 may remain constant, however the mass-flow decreases due to the decrease in density of the inlet-air 130 .
- the output of the gas turbine 105 may be determined by the mass-flow entering the gas turbine 105 ; therefore less output is produced due to the heating of the inlet-air 130 , compared to not heating of the inlet-air 130 .
- the heating of the inlet-air 130 also increases the temperature (hereinafter “compressor discharge temperature”) of the air 130 exiting the compressor 120 .
- This heated inlet-air 130 then enters the combustion system 135 .
- the heated air 130 aids in reaching the overall universal reference temperature (“firing temperature”) of the gas turbine 105 .
- the heated inlet-air 130 allows the gas turbine 105 to consume less fuel 140 to obtain the firing temperature. Here, more fuel 140 would be consumed if unheated inlet-air 130 entered the compressor 120 .
- the present invention incorporates at least one air preheater 155 , which may be installed upstream of the compressor 120 .
- the air preheater 155 may be a heat exchanger, or the like.
- the air preheater 155 may be sized to adequately heat the inlet-air 130 to a temperature that increases the turndown range.
- the temperature of the unheated inlet-air 130 may be determined by the ambient conditions or the outlet temperature of any air conditioning system (not illustrated) located upstream of the air preheater 155 .
- An embodiment of the present invention may increase the temperature of the inlet-air 130 to any temperature allowed for by the air preheater 155 .
- the increase in temperature of the inlet-air 130 may be limited by at least one of several factors, such as but not limiting of, the geometrical limitations of the air preheater 155 ; a temperature that may violate a thermal, operational, or mechanical limitation; or the like.
- the system 100 may increase the temperature of the inlet-air 130 from approximately 59 degrees Fahrenheit to approximately 120 degrees Fahrenheit.
- the inlet-air 130 may have an inlet flowrate of 3,000,000 pounds/hour.
- the system 100 illustrated in FIG. 1 , includes at least one air preheater 155 , a preheater supply line 160 ; and a preheater discharge line 165 .
- the preheater supply line 160 allows a portion of the exhaust-gas 150 , or other fluid, such as, but not limiting of, water, steam, or the like, to flow from the HRSG 110 to the air preheater 155 .
- an end of the preheater supply line 160 is connected to a portion of the HRSG 110 , where the exhaust-gas 150 may be extracted.
- the preheater supply line 160 receives a portion of the exhaust-gas 150 from the HRSG 110 .
- the exhaust-gas 150 may flow through the preheater supply line 160 , which may have an opposite end connected to a portion of the air preheater 155 .
- This first embodiment of the present invention allows a user to determine where the exhaust-gas 150 is extracted from on the HRSG 110 .
- the present invention may allow a user to optimize the location on the HRSG 110 where the exhaust-gas 150 is extracted and sent to the air preheater 155 .
- a user may consider a variety of factors when determining the optimized location on the HRSG 110 . These factors may include, for example, but not limiting of, the following. Temperature: the temperature of the fluid used to increase the temperature of the inlet-air 130 (exhaust-gas 150 , water, steam, or the like), should be higher than the maximum desired temperature that the inlet-air 130 may be raised to by the air preheater 155 .
- the maximum desired temperature might be used for sizing the air preheater 155 .
- Flow flow of the fluid should be sufficient to supply the air preheater 155 , while maintaining sufficient flow for other demands from the HRSG 110 , or the like.
- Fluid type the use of water, if available, as the fluid for increasing the temperature of the inlet-air 130 may be optimum, possibly requiring less mass-flow and a relatively smaller sized air preheater 155 .
- Energy Source the fluid may derive from an energy source that may be utilized without negatively impacting the overall benefits of heating the inlet-air 130 .
- the energy source may include, for example, but not limiting of, outlet from a condenser or fuel heater 175 ; packing flows, or the like; exhaust-gas 150 : discharge from the stack 115 ; any other energy source external to the bottoming cycle.
- an operator of the site may use a portion of the exhaust-gas 150 flowing towards the condenser (not illustrated).
- this energy may be considered ‘low value’ because the energy needed to create steam may have been already extracted.
- another site may extract the exhaust-gas 150 from another area of the HRSG 110 .
- an operator may decide that instead of restricting the flow of the exhaust-gas 150 entering a section of the HRSG 110 , divert a portion of the exhaust-gas 150 to the air preheater 155 .
- the system 100 operates while the gas turbine 105 is not at baseload.
- the present invention may divert a portion of the exhaust-gas 150 to the air preheater 155 via the preheater supply 160 .
- the exhaust-gas 150 may flow through an inlet portion of the air preheater 155 .
- the heat from the exhaust-gas 150 is transferred to, and increases the temperature of, the inlet-air 130 .
- the exhaust-gas 150 may flow through the preheater discharge line 165 to the stack 115 and/or the HRSG 110 .
- FIGS. 2 through 4 illustrate alternate embodiments of the present invention.
- a key difference between all embodiments of the present invention is the source of energy used to increase the temperature of the inlet-air 130 .
- the discussions of FIG. 2 through 4 focus on the differences between each alternate embodiment and the embodiment illustrated in FIG. 1 .
- FIG. 2 is a schematic illustrating an example of a system 200 for extending the turndown range of a gas turbine 105 in accordance with a second embodiment of the present invention.
- the primary difference between this second embodiment and the first embodiment is the addition of at least one external energy source (EES) 170 , which provides the energy for increasing the temperature of the inlet-air 130 .
- EES external energy source
- the EES 170 may provide sufficient energy to heat the inlet-air 130 to the temperature that allows for extending the turndown range. As illustrated in FIG. 2 , the EES 170 may eliminate the need for extracting the exhaust-gas 150 from the HRSG 110 . In this second embodiment, the exhaust-gas 150 may be used for other purposes and/or may flow through the stack 115 . Alternatively, the EES 170 may operate in conjunction with the embodiment of illustrated in FIG. 1 . Here, the EES 170 may operate as the primary energy system for increasing the temperature of the inlet-air 130 and the extraction from the HRSG 110 , may serve as a secondary energy system (and vice-versa).
- the EES 170 may include at least one of the following energy systems: a wind turbine, a boiler, an engine, an additional combustion turbine, an additional HRSG, a power plant, a solar energy source, geothermal energy source, fuel cell/chemical reaction, external process, and combinations thereof; none of which are illustrated in FIG. 2 .
- Each of the aforementioned energy system may indirectly or directly increase the temperature of the inlet-air 130 .
- a wind turbine may indirectly increase the temperature of the inlet fluid 130 .
- the energy generated by the wind turbine may heat water within a tank (not illustrated) integrated with the preheater supply line 160 .
- the heated water may flow through the preheater supply line 160 to the air preheater 155 .
- the heated water may flow through the preheater discharge line 165 , which may be integrated with the EES 170 .
- a boiler may directly increase the temperature of the inlet fluid 130 .
- the preheater supply line 160 may be integrated with a portion of the boiler.
- the steam or hot water generated by the boiler may flow through the preheater supply line 160 and the air preheater 155 . After flowing through the air preheater 155 , the steam or hot water may flow through the preheater discharge line 165 , which may be integrated with the EES 170 .
- FIG. 3 is a schematic illustrating an example of a system 300 for extending the turndown range of a gas turbine 105 in accordance with a third embodiment of the present invention.
- the primary difference between this third embodiment and the first embodiment is the addition of the fuel heater 175 .
- Some gas turbines 105 use heated fuel 140 as a way to increase performance.
- the fuel heater 175 commonly heats the fuel 140 on the site where the gas turbine 105 is located.
- the fuel heater 175 may have the form of a heat exchanger, or the like.
- the exhaust-gas 150 may exit the HRSG 110 via the preheater supply line 160 .
- the air preheater 155 may include multiple portions allowing for a plurality of inlet flows. As illustrated in FIG. 3 , the air preheater 155 may include a first inlet portion integrated with the fuel heater discharge line 185 , and a second inlet portion integrated with the preheater supply line 160 .
- the preheater supply line 160 may be integrated with a fuel heater supply line 180 .
- a portion of the exhaust-gas 150 may flow into the fuel heater 175 .
- Another portion of the exhaust-gas 150 may flow into the air preheater 155 .
- the exhaust-gas 150 may flow through the fuel heater discharge line 185 to the air preheater 155 .
- the exhaust-gas 150 may then flow through the preheater discharge line 165 to the stack 115 and/or the HRSG 110 , as previously described.
- FIG. 4 is a schematic illustrating an example of a system 400 for extending the turndown range of a gas turbine 105 in accordance with a fourth embodiment of the present invention.
- the primary difference between this fourth embodiment and the first embodiment is that the exhaust-gas 150 is extracted from the stack 115 , as opposed to the HRSG 110 , as illustrated in FIG. 1 .
- an end of the preheater supply line 160 is connected to a portion of the stack 115 , where the exhaust-gas 150 is extracted.
- the exhaust-gas 150 may flow through the preheater supply line 160 , which may have an opposite end connected to a portion of the air preheater 155 .
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Air Supply (AREA)
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/053,921 US20090235634A1 (en) | 2008-03-24 | 2008-03-24 | System for extending the turndown range of a turbomachine |
EP09155386.7A EP2105598A3 (en) | 2008-03-24 | 2009-03-17 | A system for extending the turndown range of a turbomachine |
JP2009069336A JP5357588B2 (ja) | 2008-03-24 | 2009-03-23 | ターボ機械のターンダウンレンジを拡張するためのシステム |
CN200910130519.0A CN101545404B (zh) | 2008-03-24 | 2009-03-24 | 用于扩大涡轮机的调节范围的系统 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/053,921 US20090235634A1 (en) | 2008-03-24 | 2008-03-24 | System for extending the turndown range of a turbomachine |
Publications (1)
Publication Number | Publication Date |
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US20090235634A1 true US20090235634A1 (en) | 2009-09-24 |
Family
ID=40527393
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
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US12/053,921 Abandoned US20090235634A1 (en) | 2008-03-24 | 2008-03-24 | System for extending the turndown range of a turbomachine |
Country Status (4)
Country | Link |
---|---|
US (1) | US20090235634A1 (ja) |
EP (1) | EP2105598A3 (ja) |
JP (1) | JP5357588B2 (ja) |
CN (1) | CN101545404B (ja) |
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US20100131169A1 (en) * | 2008-11-21 | 2010-05-27 | General Electric Company | method of controlling an air preheating system of a gas turbine |
US20100205967A1 (en) * | 2009-02-16 | 2010-08-19 | General Electric Company | Pre-heating gas turbine inlet air using an external fired heater and reducing overboard bleed in low-btu applications |
US20110088404A1 (en) * | 2009-10-16 | 2011-04-21 | General Electric Company | Reheat gas turbine |
CN102086850A (zh) * | 2009-12-04 | 2011-06-08 | 通用电气公司 | 与地热能有关的系统以及燃气涡轮发动机的操作 |
EP2333409A1 (en) * | 2009-12-04 | 2011-06-15 | Son S.R.L. | Heat recovery steam generator, method for boosting a heat recovery steam generator and related process for generating power |
CN102828830A (zh) * | 2011-06-14 | 2012-12-19 | 通用电气公司 | 用于改进组合循环发电设备的效率的系统和方法 |
US20130160424A1 (en) * | 2011-12-22 | 2013-06-27 | Alstom Technology Ltd. | Method for Operating a Combined Cycle Power Plant |
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US20140013757A1 (en) * | 2011-03-07 | 2014-01-16 | Hitachi, Ltd. | Solar Thermal Gas Turbine System |
US20140102071A1 (en) * | 2012-10-15 | 2014-04-17 | General Electric Company | System and method for heating fuel in a combined cycle gas turbine |
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US20100131169A1 (en) * | 2008-11-21 | 2010-05-27 | General Electric Company | method of controlling an air preheating system of a gas turbine |
US8483929B2 (en) * | 2008-11-21 | 2013-07-09 | General Electric Company | Method of controlling an air preheating system of a gas turbine |
US20100205967A1 (en) * | 2009-02-16 | 2010-08-19 | General Electric Company | Pre-heating gas turbine inlet air using an external fired heater and reducing overboard bleed in low-btu applications |
US8281565B2 (en) * | 2009-10-16 | 2012-10-09 | General Electric Company | Reheat gas turbine |
US20110088404A1 (en) * | 2009-10-16 | 2011-04-21 | General Electric Company | Reheat gas turbine |
WO2011067345A3 (en) * | 2009-12-04 | 2011-09-09 | Son S.R.L. | Heat recovery steam generator, method for retrofitting a heat recovery steam generator and related process for generating power |
EP2333409A1 (en) * | 2009-12-04 | 2011-06-15 | Son S.R.L. | Heat recovery steam generator, method for boosting a heat recovery steam generator and related process for generating power |
US20110132571A1 (en) * | 2009-12-04 | 2011-06-09 | General Electric Company | Systems relating to geothermal energy and the operation of gas turbine engines |
CN102086850A (zh) * | 2009-12-04 | 2011-06-08 | 通用电气公司 | 与地热能有关的系统以及燃气涡轮发动机的操作 |
US20140013757A1 (en) * | 2011-03-07 | 2014-01-16 | Hitachi, Ltd. | Solar Thermal Gas Turbine System |
CN102828830A (zh) * | 2011-06-14 | 2012-12-19 | 通用电气公司 | 用于改进组合循环发电设备的效率的系统和方法 |
US8505309B2 (en) | 2011-06-14 | 2013-08-13 | General Electric Company | Systems and methods for improving the efficiency of a combined cycle power plant |
US8844258B2 (en) | 2011-11-23 | 2014-09-30 | General Electric Company | Systems and methods for de-icing a gas turbine engine inlet screen and dehumidifying inlet air filters |
US9297316B2 (en) | 2011-11-23 | 2016-03-29 | General Electric Company | Method and apparatus for optimizing the operation of a turbine system under flexible loads |
US9046037B2 (en) * | 2011-12-22 | 2015-06-02 | Alstom Technology Ltd. | Method for operating a combined cycle power plant |
US20130160424A1 (en) * | 2011-12-22 | 2013-06-27 | Alstom Technology Ltd. | Method for Operating a Combined Cycle Power Plant |
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US9003762B2 (en) | 2012-10-02 | 2015-04-14 | General Electric Company | Turbine exhaust plume mitigation system |
US9435258B2 (en) * | 2012-10-15 | 2016-09-06 | General Electric Company | System and method for heating combustor fuel |
US20140102071A1 (en) * | 2012-10-15 | 2014-04-17 | General Electric Company | System and method for heating fuel in a combined cycle gas turbine |
US20140102105A1 (en) * | 2012-10-15 | 2014-04-17 | General Electric Company | System and method for heating combustor fuel |
US9470145B2 (en) * | 2012-10-15 | 2016-10-18 | General Electric Company | System and method for heating fuel in a combined cycle gas turbine |
US9447732B2 (en) | 2012-11-26 | 2016-09-20 | General Electric Company | Gas turbine anti-icing system |
US20140208766A1 (en) * | 2013-01-31 | 2014-07-31 | General Electric Company | Waste Heat Recovery Fuel Gas Heater Control Method and Algorithm |
US9429075B2 (en) * | 2013-01-31 | 2016-08-30 | General Electric Company | Method of operating a fuel heating system |
US20150047368A1 (en) * | 2013-08-13 | 2015-02-19 | General Electric Company | Systems and methods for controlling gas turbines |
US9644542B2 (en) | 2014-05-12 | 2017-05-09 | General Electric Company | Turbine cooling system using an enhanced compressor air flow |
CN104314691A (zh) * | 2014-10-15 | 2015-01-28 | 东方电气集团东方汽轮机有限公司 | 燃气轮机压气机进气升温方法及升温系统 |
US11859548B2 (en) | 2019-05-31 | 2024-01-02 | Mitsubishi Heavy Industries, Ltd. | Gas turbine and control method thereof, and combined cycle plant |
Also Published As
Publication number | Publication date |
---|---|
CN101545404B (zh) | 2016-05-25 |
JP5357588B2 (ja) | 2013-12-04 |
EP2105598A3 (en) | 2017-11-29 |
JP2009228678A (ja) | 2009-10-08 |
CN101545404A (zh) | 2009-09-30 |
EP2105598A2 (en) | 2009-09-30 |
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